The Boeing Company

Eric Lee Werner

Chad M Winkler

Andrew James Dorgan

Thuy Huynh

A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12&#xb0; from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.

Method and apparatus for variable exhaust nozzle exit area

A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.

Self-sealing apparatus that adjusts a throat area of a nozzle

An airflow diverter system for an aircraft may include an external aircraft surface upstream from an engine inlet and a passage having an upstream opening adjacent the engine inlet. The passage may be configured to channel boundary airflow from the external aircraft surface away from the engine inlet. The diverter system may include an occlusion device configured to selectively open and close the opening to the passage.

Variable geometry flush boundary diverter

A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12&#xb0; from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.

Method and apparatus for nozzle thrust vectoring

A variable area mechanism and methods are disclosed. A movable surface comprising a contoured interface surface is operable to rotate about an off-body axis-of-rotation such that the movable surface expands from and retracts into an angle notched surface.

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Des Peres, MO, United States of America

Eric Lee Werner